CN114722686A - Method for designing and optimizing lifting lug of large equipment based on finite element analysis - Google Patents
Method for designing and optimizing lifting lug of large equipment based on finite element analysis Download PDFInfo
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Abstract
The invention provides a design and optimization method of a lifting lug of large equipment based on finite element analysis, which is characterized in that a lifting integral analysis finite element model, a lifting lug strength and local stress refining model are established, the mass of the finite element model is adjusted by introducing a gravity acceleration amplification factor, and a proper lifting point position is determined according to the integral stress and deformation of the equipment. According to the invention, based on the boundary data mapping between the two models, the number of computational grids is reduced, and the computational efficiency and precision are improved; the strength of the lifting lug is calculated based on a strength theory, the stress of the shell ring thin film and the surface bending stress in the refined model are calculated based on a path stress linearization theory, stress evaluation is carried out, and the size of the lifting lug is optimized. According to the invention, the design optimization is carried out on the lifting point position of the equipment by a finite element method, the size and shape difference of the lifting lugs is fully considered, the self strength of the lifting lugs and the local stress of the shell ring in the lifting process are accurately calculated, and the design precision and efficiency of the lifting lugs of large-scale equipment are improved.
Description
Technical Field
The invention belongs to the technical field of structural design of lifting lugs of large equipment, and particularly relates to a method for designing and optimizing a lifting lug of large equipment based on finite element analysis.
Background
With the vigorous development of the national energy and chemical field, chemical equipment gradually develops towards the direction of heavy and large scale, and standardized lifting lugs which are specified in a standard and do not need special design are difficult to meet the lifting requirements of the large equipment; the type and the form of the non-standard lifting lug are complex and changeable, and the problems of large error, poor economy caused by over-conservative design and the like exist when the traditional standard method is used for designing and checking the lifting lug. Therefore, in order to ensure the safety and stability of the equipment hoisting process, the reasonable and reliable hoisting point position and the economic and reasonable lug size, the design and optimization research of the nonstandard lugs of large-scale equipment is necessary.
Compared with a standard lifting lug, the non-standard lifting lug often needs to be welded with an additional auxiliary reinforcing plate, and the auxiliary influence often cannot be considered during the traditional lifting lug strength design calculation, so that the calculation deviation is large. For a lifting lug with the nominal lifting weight of more than 300t or the corresponding cylinder section with a thin thickness, the strength of the lifting lug needs to be checked and the local stress of the cylinder section needs to be calculated, while the traditional lifting lug design method is over simplified in the process of calculating the local stress and has the problem that the size of part of the lifting lug cannot be calculated. Meanwhile, in the hoisting process, the load size and the load angle borne by the lifting lug are changed all the time, and the traditional lifting lug design method only considers two working conditions of 0-degree lifting angle and 90-degree lifting angle of the equipment, so that the stress of the lifting lug and the local stress change of the shell ring in the hoisting process cannot be analyzed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a design and optimization method of a lifting lug of large equipment based on finite element analysis, which improves the design accuracy and efficiency of the lifting lug of the large equipment to a greater extent, optimizes the size of the lifting lug and saves the material and processing cost.
The present invention achieves the above-described object by the following technical means.
A design and optimization method of a lifting lug of large equipment based on finite element analysis comprises the following steps:
step 1: simplifying the equipment into a symmetrical rotating body, and establishing a large-scale equipment hoisting integral finite element model A based on equipment size parameter information and material mechanics parameter information;
step 2: determining the positions and the number of lifting points according to a field hoisting scheme, simplifying the lifting lugs into concentrated mass points, setting the value and the direction of the gravity acceleration in a finite element model A, performing pre-hoisting simulation by adopting a finite element method, and deriving load counter force borne by the concentrated mass points, wherein the direction of the load counter force is opposite to the direction of the gravity acceleration;
and step 3: introducing a gravity acceleration amplification factor, and adjusting the mass of a finite element;
and 4, step 4: carrying out finite element simulation in the hoisting process, calculating according to a finite element model A to obtain an integral stress cloud picture and a deformation cloud picture of the equipment, comparing the maximum stress and the maximum deformation with a standard limit value, and readjusting the position of the hoisting point until the position meets the limit value when the overrun condition occurs; then, deriving a projection plane formed by projecting the peripheral region of the concentrated mass points to the equipment cylinder body along the normal direction, and then deriving all node reaction force data on the peripheral boundary of the projection plane;
and 5: preliminarily drawing up the parameterized size of the lifting lug of the equipment according to the actual quality of the equipment, inputting the parameterized size into a parameterized modeling platform, and establishing a locally refined finite element model B of the lifting lug;
step 6: mapping the node reaction force data of the boundary obtained by calculation according to the finite element model A into the boundary of the finite element model B, and carrying out numerical simulation analysis on the finite element model B;
and 7: and (4) calculating to obtain a new integral stress cloud picture and a new deformation cloud picture of the equipment according to the finite element model B, analyzing whether the strength of the lifting lug and the local stress of the shell ring meet the requirements, if not, repeating the steps 5 and 7, and redesigning the size of the lifting lug until the requirements are met.
Further, in the step 3, the gravity acceleration amplification factor is calculated by the following formula:
wherein the content of the first and second substances,
is a gravity acceleration amplification factor, and is,
the actual hoisting quality is obtained;
the number of the hanging points is;
load counter force borne by the concentrated mass points;
is the acceleration of gravity;
is the dynamic load coefficient;
is unevenA balance coefficient;
and multiplying the gravity acceleration by a gravity acceleration amplification coefficient, and then endowing the gravity acceleration multiplied by the gravity acceleration amplification coefficient to the finite element model A again to realize the mass adjustment of the finite element.
Further, in the step 6, the geometric dimensions of the boundaries of the finite element model a are consistent with those of the boundaries of the finite element model B, and the mesh sizes are inconsistent; and establishing a linear interpolation function according to the coordinate relation of the grid nodes on the boundary of the finite element model B relative to the grid nodes on the boundary of the finite element model A, and completing the mapping of node reaction force data between the finite element model A and the finite element model B.
Further, in the step 7, when analyzing the local stress of the shell ring, three grid nodes with top three ranked stress values of the Tresca stress value on the surface of the shell ring are searched first, and the searched grid nodes are used for making straight lines along the thickness direction of the shell ring to obtain three stress classification lines; then searching three grid nodes with the stress values of Tresca ranked in the first three on the surface of the lifting lug base plate on the finite element model B, making a straight line from the searched grid nodes along the thickness direction of the lifting lug base plate to obtain three stress classification lines, and obtaining six stress classification lines in total;
and then, deriving the Tresca stress of all grid nodes on six stress classification lines, respectively carrying out stress linearization on six stress components of the normal stress and the shear stress in the direction of X, Y, Z to obtain the film stress and the bending stress of each component, and then calculating the large main stress, the medium main stress and the small main stress through a third strength theory to further obtain the total film stress and the bending stress, so as to carry out stress evaluation.
Further, the stress linearization is calculated as follows:
wherein the content of the first and second substances,
in order to be the stress of the thin film,
in order to be subjected to a bending stress,
in order to be the actual stress,
is the X-axis coordinate of the local coordinate system,
the length of the stress classification line.
Further, the characteristic equations corresponding to the large principal stress, the medium principal stress and the small principal stress are as follows:
wherein:
in the formula (I), the compound is shown in the specification,
、
、
respectively representing a positive stress in the direction of X, Y, Z,
、
、
respectively, the shear stress in the direction of X, Y, Z,
、
、
the symbols are given in the expression of a characteristic equation formula;
further, in the step 7, when the strength of the lifting lug is analyzed, the maximum Tresca stress of the lifting lug is extracted according to the stress cloud picture and is compared with the yield strength of the material, and when the maximum Tresca stress is greater than the yield strength of the material, the size of the lifting lug is redesigned.
Further, the length and the width of the projection plane are equal to 2 times of the width of the lifting lug.
The invention has the following beneficial effects:
the position of the lifting lug of the large-scale equipment is optimized by a finite element method so as to ensure the integral strength and stability of the equipment. According to the method, the size and shape difference of the non-standard lifting lug are fully considered, the self strength of the lifting lug and the local stress of the shell ring in the lifting process can be accurately calculated, the design precision and efficiency of the lifting lug of the large-scale equipment can be improved, the size of the lifting lug is optimized, the material and processing cost are saved, and basis and guidance are provided for the design and optimization of the lifting lug of the chemical equipment.
The lifting lug design and optimization method provided by the invention effectively analyzes the lifting lug stress and the barrel section local stress change in the lifting process, respectively establishes the barrel whole model and the lifting lug local refining model, establishes the boundary counter force between the two models and carries out mapping transmission, realizes effective control of the number of unit grids, and greatly improves the calculation efficiency under the condition of ensuring the calculation precision. And a gravity acceleration amplification factor is introduced to optimize the finite element quality, and the non-standard lifting lug designed based on the invention has small structural error and is safer and more reliable. In addition, the method provided by the invention can be used for not only large-scale chemical equipment, but also other lifting lugs for large-scale equipment in an optimized design project, has a wide application range, and is worthy of popularization and use.
Drawings
FIG. 1 is a flow chart of a design optimization method of a lifting lug of large equipment based on finite element analysis, which is disclosed by the invention;
FIG. 2 is a schematic view of a finite element model A for hoisting a large-scale device according to the present invention;
FIG. 3 is a partial enlarged view of a shell ring of a hoisting point region in the finite element model A;
FIG. 4 is a schematic diagram of a partially refined finite element model B of the lifting lug according to the present invention;
FIG. 5 is a schematic diagram of a boundary data mapping relationship between a finite element model A and a finite element model B.
In the figure: 1-a projection plane; 2-ear hanging point; 3-a first boundary; 4-a second boundary; 5-a third boundary; 6-fourth boundary; 7-fifth boundary; 8-sixth boundary; 9-seventh boundary; 10-eighth boundary; 11-end enclosure; 12-shell ring; 13-skirt; 14-shackle tie plate.
Detailed Description
The invention will be further described with reference to the following figures and specific examples, but the scope of the invention is not limited thereto.
The design optimization method of the lifting lug of the large-scale equipment based on finite element analysis is shown in figure 1 and specifically comprises the following steps:
step 1: obtaining dimension parameter information according to a CAD design drawing of the equipment, wherein the dimension parameter information in the embodiment comprises the dimension of an end socket 11, the nominal diameter and the thickness of the equipment, the nominal diameter and the thickness of a shell ring 12 and the dimension of a skirt 13 of the equipment; obtaining the mechanical parameters of the equipment according to the standard documents and the mechanical tests, wherein the mechanical parameters comprise elastic modulus, Poisson's ratio, yield strength and yield strain;
simplifying the equipment into symmetrical rotating bodies, inputting size parameter information into a parametric modeling platform, establishing a large-scale equipment hoisting integral finite element model A shown in figure 2, and simultaneously inputting material mechanical parameters and giving the finite element model A, wherein the integral size of the equipment is considered, a large grid is adopted in the finite element model A for facilitating the analysis of the integral stress and deformation of the equipment, and the average size of the grid of the finite element model A is controlled within 0.2 multiplied by 0.2 m.
Step 2: determining the positions of lifting points and the number of the lifting points according to a field lifting scheme, wherein the positions of the lifting points comprise the distance from the lifting points to the top of the equipment and the distance from the lifting points to the bottom of the equipment; as shown in FIG. 2, the lifting lug is simplified to be a concentrated mass point, gravity acceleration in a finite element model AaSet at 9.8m/s2And the direction is the-Y direction, the pre-hoisting simulation is carried out by adopting a finite element method, and then the load counter force in the Y direction received by the concentrated mass point is derived.
And step 3: since the simplification of the device in the modeling process may cause an error between the finite element mass (i.e., the calculated mass) and the actual mass, the present embodiment introduces a gravity acceleration amplification factor, and the gravity acceleration amplification factor is calculated by the following formula:
wherein the content of the first and second substances,
is a gravity acceleration amplification factor, and is,
the actual hoisting quality is obtained;
the number of the hanging points is;
the load counter force in the Y direction received by the concentrated mass point is obtained;
taking 9.8m/s as gravity acceleration2；
Taking 1.2 as the dynamic load coefficient;
taking the coefficient of unbalance as 1.125;
and multiplying the gravity acceleration by the gravity acceleration amplification coefficient obtained by calculation, then endowing the gravity acceleration amplification coefficient to the finite element model A again, and adjusting the mass of the finite element to reduce the error between the mass of the finite element and the actual mass.
And 4, step 4: carrying out finite element simulation in the hoisting process, wherein the finite element simulation mainly comprises initial hoisting simulation, equipment attitude adjustment (including rotation and translation) and equipment final installation attitude simulation; then, calculating according to the finite element model A to obtain an integral stress cloud picture and a deformation cloud picture of the equipment, comparing the maximum stress and the maximum deformation with a standard limit value, repeating the step 2 if an overrun condition occurs, and readjusting the position of the lifting point until the stress and the deformation are qualified;
then, a projection plane 1 (the arrow direction on the surface of the shell section 12 in fig. 2 represents the normal direction) formed by projecting the peripheral area of the concentrated mass point (namely, the lifting lug point 2) to the equipment shell body along the normal direction in the hoisting process is derived, and repeated experimental research shows that the boundary effect influence is minimum when the length and the width of the projection plane 1 are both 2 times of the width of the lifting lug; next, all the node reaction force data on the peripheral boundary of the projection plane 1 are derived, and as shown in FIG. 3, the peripheral boundary of the projection plane 1 includes a first boundary 3, a second boundary 4, a third boundary 5, and a fourth boundary 6, and the node reaction force data includes the X-direction reaction force CFxY-squareCounter force CFYZ-direction reaction force CFZ。
And 5: preliminarily drawing up the parametric dimension of the lifting lug of the equipment according to the actual quality of the equipment, inputting the parametric modeling platform, and establishing a local refined finite element model B of the lifting lug shown in figure 4, wherein in order to improve the subsequent stress linearization computing precision, the finite element model B adopts a small grid, the grid dimension of the finite element model B is 0.05 multiplied by 0.05m, and the grid number of the finite element model B can also be effectively controlled due to the small scale of the finite element model B, so that the computing efficiency can be ensured. In addition, the types of the lifting lugs mainly comprise top plate type lifting lugs, horizontal equipment plate type lifting lugs, side wall plate type lifting lugs, shaft type lifting lugs and tail lifting lugs, and the parameterized sizes comprise plate type lifting lug hole diameters, shaft type lifting lug pipe shaft outer diameters, mooring cable ring plate outer diameters, plate type lifting lug thicknesses or shaft type lifting lug pipe shaft thicknesses and backing plate thicknesses; in the embodiment, preferably, a shaft-type lifting lug is taken as an example to establish a finite element model B; the finite element model B includes a cylindrical shell 12 having a size corresponding to the projection plane 1, in addition to the lifting lugs and the connecting members.
And 6: as shown in fig. 5 (the numerical labels in fig. 5 all indicate the mesh nodes on the first boundary 3), the node reaction force data of the boundary calculated according to the finite element model a is mapped into the boundary of the finite element model B, that is, the node reaction force data of the first boundary 3 of the finite element model a is transmitted to the fifth boundary 7 of the finite element model B, the node reaction force data of the second boundary 4 of the finite element model a is transmitted to the sixth boundary 8 of the finite element model B, the node reaction force data of the third boundary 5 of the finite element model a is transmitted to the seventh boundary 9 of the finite element model B, and the node reaction force data of the fourth boundary 6 of the finite element model a is transmitted to the eighth boundary 10 of the finite element model B;
because the geometric dimensions of the first boundary 3 and the fifth boundary 7, the second boundary 4 and the sixth boundary 8, the third boundary 5 and the seventh boundary 9, and the fourth boundary 6 and the eighth boundary 10 are all consistent, but the mesh dimensions are all inconsistent, the present embodiment establishes a linear interpolation function through the coordinate relationship of the mesh nodes of the boundary of the finite element model B relative to the mesh nodes of the boundary of the finite element model a, and completes the mapping of node reaction force data between the finite element model a and the finite element model B; for example, as shown in fig. 5, the load of the mesh node C on the fifth boundary 7 is determined by jointly interpolating the loads of the four mesh nodes 202, 203, 302, 303 on the first boundary 3.
And 7: calculating to obtain a new integral stress cloud picture and a new deformation cloud picture of the equipment according to the finite element model B, firstly analyzing the strength of the lifting lug, extracting the maximum Tresca stress of the lifting lug according to the stress cloud picture, comparing the maximum Tresca stress with the yield strength of the material, and redesigning the size of the lifting lug when the maximum Tresca stress is greater than the yield strength of the material;
then analyzing the local stress of the shell ring 12, as shown in fig. 4, firstly searching three grid nodes of the top three of the rank of the surface Tresca stress value of the shell ring 12 (the surface Tresca stress values of the shell ring 12 are sorted from large to small), making a straight line along the thickness direction of the shell ring 12 by the searched grid nodes to obtain three stress classification lines, then searching three grid nodes of the top three of the rank of the surface Tresca stress value of the lifting lug base plate 14 (the surface Tresca stress values of the lifting lug base plate 14 are sorted from large to small), making a straight line along the thickness direction of the lifting lug base plate 14 by the searched grid nodes to obtain three stress classification lines, and obtaining six stress classification lines in total; then, the Tresca stresses of all grid nodes on the six stress classification lines are derived, the six stress components of the normal stress and the shear stress in the X, Y, Z direction are subjected to stress linearization respectively, and the film stress and the bending stress of each component are obtained, and the stress linearization calculation is as follows:
wherein, the first and the second end of the pipe are connected with each other,
in order to be the stress of the thin film,
in order to be subjected to a bending stress,
in order to be the actual stress,
is the X-axis coordinate of the local coordinate system,
is the length of the stress classification line;
and calculating the large main stress, the medium main stress and the small main stress by a third intensity theory to further obtain the total film stress and the total bending stress, wherein the characteristic equations corresponding to the large main stress, the medium main stress and the small main stress are as follows:
wherein:
wherein the content of the first and second substances,
、
、
respectively representing the positive stress in the direction X, Y, Z,
、
、
respectively representing the shear stress in the direction of X, Y, Z;
、
、
symbols given in the expression of the characteristic equation formula have no practical significance, so that the expression of the characteristic equation formula is simpler;
and 8: and (4) evaluating the stress of the film and the bending stress according to the stress and the bending stress calculated in the step (7), wherein the evaluation standard is as follows: the film stress is less than 1.5 times of the allowable strength of the material, and the film stress and the bending stress are less than 3 times of the allowable strength of the material; when the calculated stress data is larger than the standard requirement, the size of the lifting lug needs to be increased, and the steps 5, 7 and 8 are repeated to redesign the size of the lifting lug until the stress data meets the requirement; and when the calculated stress data is far lower than the standard requirement, the size of the lifting lug needs to be reduced, and the steps 5, 7 and 8 are repeated to redesign the size of the lifting lug until the stress data meets the requirement. When the calculated stress data is far lower than the standard requirement, the difference value between the stress data and the standard requirement is selected according to the actual design requirement.
In this embodiment, fig. 2 is an overall finite element model of a certain large-scale device, which is preferably shown, and the overall finite element models established by the sizes of other large-scale devices can be designed by applying the method provided by the present invention; fig. 4 is a partially refined finite element model of a lifting lug, which is only shown as a preferred example, and detailed finite element models established by lifting lug sizes of other large-scale equipment can be designed by applying the method provided by the invention.
The present invention is not limited to the above-described embodiments, and any obvious improvements, substitutions or modifications can be made by those skilled in the art without departing from the spirit of the present invention.
Claims (8)
1. A design and optimization method of a lifting lug of large equipment based on finite element analysis is characterized by comprising the following steps:
step 1: simplifying the equipment into a symmetrical rotating body, and establishing a large-scale equipment hoisting integral finite element model A based on equipment size parameter information and material mechanics parameter information;
step 2: determining the positions and the number of lifting points according to a field hoisting scheme, simplifying the lifting lugs into concentrated mass points, setting the value and the direction of the gravity acceleration in a finite element model A, performing pre-hoisting simulation by adopting a finite element method, and deriving load counter force borne by the concentrated mass points, wherein the direction of the load counter force is opposite to the direction of the gravity acceleration;
and step 3: introducing a gravity acceleration amplification factor, and adjusting the mass of a finite element;
and 4, step 4: carrying out finite element simulation in the hoisting process, calculating according to a finite element model A to obtain an integral stress cloud picture and a deformation cloud picture of the equipment, comparing the maximum stress and the maximum deformation with a standard limit value, and readjusting the position of the hoisting point until the position meets the limit value when the overrun condition occurs; then, deriving a projection plane (1) formed by projecting the peripheral region of the concentrated mass points to the equipment cylinder body along the normal direction, and then deriving all node reaction force data on the peripheral boundary of the projection plane (1);
and 5: preliminarily drawing up the parameterized size of the lifting lug of the equipment according to the actual quality of the equipment, inputting the parameterized size into a parameterized modeling platform, and establishing a locally refined finite element model B of the lifting lug;
step 6: mapping the node reaction force data of the boundary obtained by calculation according to the finite element model A into the boundary of the finite element model B, and carrying out numerical simulation analysis on the finite element model B;
and 7: and (4) calculating according to the finite element model B to obtain a new integral stress cloud chart and a new deformation cloud chart of the equipment, analyzing whether the strength of the lifting lug and the local stress of the shell ring (12) meet the requirements, if not, repeating the steps 5 and 7, and redesigning the size of the lifting lug until the requirements are met.
2. The method for designing and optimizing a lifting lug of large equipment based on finite element analysis according to claim 1, wherein in the step 3, the gravity acceleration amplification factor is calculated by the following formula:
wherein, the first and the second end of the pipe are connected with each other,
is a gravity acceleration amplification factor, and is,
the actual hoisting quality is obtained;
the number of the hanging points is;
load counter force borne by the concentrated mass points;
is the acceleration of gravity;
is the dynamic load coefficient;
is the unbalance coefficient;
and multiplying the gravity acceleration by a gravity acceleration amplification coefficient, and then endowing the gravity acceleration to the finite element model A again to realize the mass adjustment of the finite element.
3. The method for designing and optimizing a lifting lug of large equipment based on finite element analysis according to claim 1, wherein in the step 6, a linear interpolation function is established according to the coordinate relationship of the grid nodes of the boundary of the finite element model B relative to the grid nodes of the boundary of the finite element model A, and the mapping of node reaction force data between the finite element model A and the finite element model B is completed.
4. The method for designing and optimizing a lifting lug of large equipment based on finite element analysis according to claim 1, wherein in the step 7, when the local stress of the shell ring (12) is analyzed, three grid nodes ranked in the first three of the Tresca stress values on the surface of the shell ring (12) are searched, and a straight line is drawn from the searched grid nodes along the thickness direction of the shell ring (12) to obtain three stress classification lines; then searching three grid nodes with the stress values of Tresca ranked in the first three on the surface of the lifting lug base plate (14) on the finite element model B, and drawing straight lines on the searched grid nodes along the thickness direction of the lifting lug base plate (14) to obtain three stress classification lines, and obtaining six stress classification lines in total;
and then, deriving the Tresca stress of all grid nodes on six stress classification lines, respectively carrying out stress linearization on six stress components of the normal stress and the shear stress in the direction of X, Y, Z to obtain the film stress and the bending stress of each component, and then calculating the large main stress, the medium main stress and the small main stress through a third strength theory to further obtain the total film stress and the bending stress, so as to carry out stress evaluation.
5. The finite element analysis-based large equipment lifting lug designing and optimizing method according to claim 4, wherein the stress linearization is calculated as follows:
wherein, the first and the second end of the pipe are connected with each other,
in order to be the stress of the thin film,
in order to have a bending stress, it is preferable that,
in order to be the actual stress,
is the X-axis coordinate of the local coordinate system,
the length of the stress classification line.
6. The method for designing and optimizing a lifting lug of large equipment based on finite element analysis according to claim 5, wherein the characteristic equations corresponding to the large principal stress, the medium principal stress and the small principal stress are as follows:
wherein:
in the formula (I), the compound is shown in the specification,
、
、
respectively representing a positive stress in the direction of X, Y, Z,
、
、
respectively, the shear stress in the direction of X, Y, Z,
、
、
the symbols are given in the expression of a characteristic equation formula;
7. the finite element analysis-based method for designing and optimizing a shackle of large equipment according to claim 1, wherein in the step 7, when the shackle strength is analyzed, the maximum Tresca stress of the shackle is extracted according to the stress cloud chart and compared with the yield strength of the material, and when the maximum Tresca stress is greater than the yield strength of the material, the shackle size is redesigned.
8. A finite element analysis based lifting lug design and optimization method for large equipment according to claim 1, characterized in that the length and width of the projection plane (1) are equal to 2 times the lifting lug width.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116663354A (en) * | 2023-05-12 | 2023-08-29 | 中国建筑第二工程局有限公司 | Sheet deformation calculation method, apparatus, device, and storage medium |
| CN116933429A (en) * | 2023-07-28 | 2023-10-24 | 招商局重工（江苏）有限公司 | FPSO lower slip ring hoisting, transferring and deformation control method |
| WO2024017240A1 (en) * | 2022-07-19 | 2024-01-25 | 中广核工程有限公司 | Steel lining module construction method, hoisting tool and limiting tool |
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